EP2028099B1 - Système de propulsion avec une hélice à pas variable - Google Patents

Système de propulsion avec une hélice à pas variable Download PDF

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Publication number
EP2028099B1
EP2028099B1 EP07016481A EP07016481A EP2028099B1 EP 2028099 B1 EP2028099 B1 EP 2028099B1 EP 07016481 A EP07016481 A EP 07016481A EP 07016481 A EP07016481 A EP 07016481A EP 2028099 B1 EP2028099 B1 EP 2028099B1
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EP
European Patent Office
Prior art keywords
drive system
blades
system per
drive
gears
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP07016481A
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German (de)
English (en)
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EP2028099A1 (fr
Inventor
Ingo Bader
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Bader Ingo
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Bader Ingo
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Application filed by Bader Ingo filed Critical Bader Ingo
Priority to EP07016481A priority Critical patent/EP2028099B1/fr
Priority to DE502007005052T priority patent/DE502007005052D1/de
Priority to AT07016481T priority patent/ATE481312T1/de
Publication of EP2028099A1 publication Critical patent/EP2028099A1/fr
Application granted granted Critical
Publication of EP2028099B1 publication Critical patent/EP2028099B1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H3/00—Propeller-blade pitch changing
    • B63H3/06—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/44—Blade pitch-changing mechanisms electric

Definitions

  • the invention relates to a drive system with a variable pitch propeller, more particularly to such a drive system having two electric motors.
  • Variable pitch propulsion systems are used as a propulsion system for ships and aircraft, for example.
  • drive systems are also used for facilities that serve less the propulsion, but mainly a control, for example in a bow thruster of a ship or as a tail rotor of a helicopter.
  • facilities for pumping liquids or gases from propulsion system propulsion systems such as pumps, turbines or fans, also make use of it. All systems mentioned are drive systems in the sense of this application.
  • variable pitch propellers have a number of leaves that act on the surrounding medium, usually water or air, and their angle of attack can be adjusted. By adjusting the angle of attack, the variable pitch propeller can be adapted to different conditions. It can be optimal flow dynamic properties of the variable pitch propeller depending on the flow rate, the speed and the available torque reach.
  • variable pitch propeller with an electric motor is becoming increasingly important because more powerful and lighter electric motors, in particular due to the lower cost availability of high quality permanent magnets, and also more powerful and compact electrical energy sources are available.
  • An electric drive is thus a low-emission alternative to internal combustion engines for many applications, such as powered gliders, microlights and model airplanes or helicopters.
  • the blades which are mounted so as to be rotatable about their longitudinal axis, are provided with a lever in the region of their root, the position of which sets the blade adjustment angle.
  • a special mechanism is required, which rotates together with the leaves and which usually articulates the lever with a kind of control cam. Due to this mechanical construction, the adjustment range of the blade adjustment angle is limited.
  • Out DT 2 404 694 A1 is known a drive for a toy plane, in which each blade of a variable pitch propeller has at its root a bevel gear.
  • On the symmetry axis of the variable pitch propeller are two more bevel gears arranged, which are in engagement with the bevel gear located on the blade root, so that a relative rotation of the two bevel gears arranged on the axis of symmetry causes a rotation of the blade about its longitudinal axis, ie an adjustment of the blade pitch.
  • the second arranged on the axis of symmetry bevel gear is coupled to the first via a spring.
  • the relative rotation of the two bevel gears is also limited by two stops, corresponding to a minimum and a maximum blade pitch.
  • Out EP 0 928 738 A2 is known a drive with a variable pitch propeller for a ship.
  • the blades of the variable pitch propeller are rotatably mounted at their outer end within an annular rotor of an electric motor.
  • the blades have an axis arranged along their longitudinal axis, whose outer end is rotatably mounted in the rotor of the drive motor.
  • At a distance from the longitudinal axis of each blade has a pin which is guided in a direction perpendicular to the rotational direction aligned slot in a second, annular rotor of a second electric motor.
  • both motors are designed as brushless internal rotor, ie the stator windings are located outside the rotor.
  • the Bladeinstellwinkel can be adjusted by a relative rotation of the second rotor relative to the first rotor.
  • each blade having a bevel gear at the root, which is rotated by two electrically driven bevel gears to adjust the blade pitch.
  • the drive the two electrically driven bevel gears is done by a single electric motor. This has the consequence that the Blattanstellwinkel can only be limited and adjusted to the same extent for each sheet.
  • connection of the electric motors with the drive gears can be done by a direct mechanical connection or via a transmission.
  • two drive gears which are driven independently by two electric motors, an unlimited range of adjustment of the blade pitch is possible.
  • the leaves can also be adjusted so that the angle between the leaves and the plane swept by the leaves reverses. This achieves a thrust reversal. It is also possible to change the angle of attack by 180 ° and at the same time reverse the direction of rotation of the propeller. This allows the drive even with leaves whose pitch changes with the distance from the axis of symmetry as a result of a twisted shape of the sheet in both directions with a flow dynamic optimum blade profile, so that a uniformly high efficiency is achieved.
  • variable pitch propeller which manages without separate adjustment lever or complicated cams.
  • the functionality of these now expendable components is taken over by the control of the electric motors, i.
  • the control of the blade pitch is carried out without additional mechanical components by a suitable control of the electric motors.
  • a separate drive which would be required especially for the adjustment, can also be omitted.
  • the symmetrical arrangement of the two drive gears on both sides of the longitudinal axis of the leaves also reduces the mechanical stress, in particular the storage of the leaves.
  • three or more blades are provided. This ensures that the two drive gears are automatically secured by the engagement with the arranged on the blades gears against tilting with respect to the axis of symmetry.
  • the gears on the blades and the two drive gears are designed as bevel gears, or there are on the leaves spur gears are used, which cooperate with crown wheels on the two drive gears. Both alternatives represent a particularly advantageous embodiment of the gear mechanism for the pitch adjustment.
  • the gears are disposed on the blades at the outer end of the blades and the drive gears are annular.
  • the blades of the variable pitch propeller are thus inside the gear mechanism for pitch adjustment. It is thereby possible to carry out the hub located in the center of the variable pitch propeller particularly compact.
  • a further preferred embodiment provides that the electric motors are brushless internal rotors whose rotors are connected to the drive gears, so that the stator windings of the electric motors are arranged outside the area swept by the blades.
  • This embodiment is particularly advantageous when the drive system is to be used within a pipe. In this case, all electrical connections are accessible from the outside.
  • Another advantage of this embodiment, in which the electrical and mechanical components are separated from each other, is that the air gap between the rotor and the stator of the brushless internal rotor can be met even when used under water by the medium surrounding the variable pitch propeller.
  • the gears are arranged on the blades at the ends of the blades facing the axis of symmetry.
  • the gears are thus at the blade roots.
  • This embodiment is particularly advantageously combined with electric motors which are brushless external rotors whose rotors are each connected to a drive gear so that the stator windings of the electric motors are arranged within the area swept by the blades. This results in a particularly compact design, in which concentrate all electrical components in the vicinity of the axis of symmetry.
  • the runners of the electric motors are mounted on a common, hollow axle.
  • the hollow design In addition to the structural simplification with a common axis allows the hollow design to lead to the one motor leading supply lines within the axis, so that the control of both motors can easily be done from one side.
  • the two drive gears integral with the motor bells of the two runners. It makes it a special one achieved simple mechanical design and optimum connection of the drive gears with the runners.
  • an electronic control for controlling the electric motors is provided.
  • a separate control can be used for each electric motor.
  • the relative rotational movement of the two electric motors which is important for the adjustment of the blade pitch angle, can be controlled by a single central control.
  • the control is carried out essentially by specifying a corresponding with the desired blade pitch phase relationship between the two impressed in the stator windings of the two motors currents or voltages.
  • the electronic control has angle sensors for determining the angular position of the electric motors. From the angular position of the two electric motors can also be closed to the relative angular position of both motors, so that the present blade pitch can be determined from the signals of the angle sensors. The corresponding signals thus represent an important quantity which is made available to the electronic control.
  • zero-crossing sensors are provided as angle sensors. These are particularly simple sensors that do not measure the exact angular position of the rotor of the electric motors during the rotational movement, but only give a signal indicating the passage through a zero-angle position. Because of this zero-crossing signal, the electronic controller can calculate the speed of the respective rotor and also the angular position of the rotor at a certain time.
  • the electric motors are operable in the generator mode.
  • electrical energy can be obtained from the rotational movement of the variable pitch propeller.
  • a control unit gives each engine a specific torque and monitors the relative angular position of both engines.
  • electrical energy can be recovered with optimum efficiency.
  • the energy obtained can be used advantageously for charging electrical energy source.
  • this embodiment is particularly useful in gliders that are equipped with the drive system according to the invention.
  • the generator operation can be used advantageously, for example, to achieve a controllable braking effect.
  • the leaves have an asymmetrical profile.
  • An asymmetric blade profile is optimized for a specific direction of flow. In conjunction with the wide blade pitch range of the invention, this optimized blade profile can be used to advantage even when thrust reversal is desired.
  • FIG. 1 Drive system shown has a variable pitch propeller with an axis of symmetry 1, which has three leaves 10.
  • the illustrated drive system is intended for use as an airscrew.
  • Each of the leaves has a bevel gear 11 near its root.
  • Through the bevel gear through a longitudinal axis, not shown, which is rotatably mounted in a hub member 20 and secured against displacement in the direction of its longitudinal axis.
  • the hub member 20 is rotatably supported on the hollow shaft 30 by means of a ball bearing, not shown.
  • a first electric motor which is a brushless external rotor. It has a rotor 41, which is rotatably mounted on the hollow shaft 30, and a stator 42.
  • the stator 42 is fixedly connected to the axis 30 and has 18 stator windings 43.
  • the electric motor 40 is fixedly connected to the bevel gears 11 of the blades 10 side facing the rotor 41 with a drive gear 45, which is also designed as a bevel gear.
  • a second electric motor can be seen, which corresponds to the first electric motor 40.
  • a second drive gear 55 is arranged, which also faces the bevel gears 11 of the blades 10.
  • the two drive gears 45 and 55 are engaged with the bevel gears 11 of the blades 10 so that relative rotational movement of the two drive gears 45 and 55 results in rotation of the blades 10 about their longitudinal axis.
  • stator windings 48 In the block diagram of FIG. 2 can be seen at 40 and 50, the two electric motors, which are symbolized by their stator windings 48.
  • Each of the stator windings 48 optionally comprises a plurality of stator windings 43 FIG. 1 that are interconnected and powered together.
  • three-phase leads 70 each lead to the stator windings.
  • Each of the three phases of each of the two motors is independently powered by a bridge circuit of two semiconductor switches 72.
  • the semiconductor switches 72 are driven by a central electronic control unit 80 via the control lines connected to the outputs 82 of the control unit.
  • Each of the two motors is associated with a zero-crossing sensor 60 which is connected to the three-phase supply line 70 and from the currents or voltages in these leads detected zero-crossing signals, which are passed via the lines 74 to the inputs 84 of the central control unit 80.
  • the control unit 80 thus receives feedback on the angular position of the rotor of the two electric motors, so that a targeted control of this angular position on the semiconductor switches 72 for targeted adjustment of the blade pitch is possible.
  • the invention also relates to a method for adjusting the angle of attack of a propeller, which is obtained by the position difference between two coaxially operated electric motors.
  • the method avoids the disadvantage of some other known devices in which the blade adjustment only about the centrifugal force is possible.
  • Another disadvantage of other blade pitchers is that they require additional external equipment, such as servos or hydraulic actuators.
  • the device can be constructed of a commercially available brushless external rotor, which consists of a motor shaft, a stator and a motor bell and is extended so that a second stator and a second bell are coaxially mounted on the central motor axis.
  • a commercially available brushless external rotor which consists of a motor shaft, a stator and a motor bell and is extended so that a second stator and a second bell are coaxially mounted on the central motor axis.
  • the motor axis must be made hollow in this modification to accommodate the lines of the power supply for the motor winding.
  • the feet of propeller blades (two or more), which are provided for example with a bevel pinion, are mounted on bevel gears in the manner of a differential gear between the two motor bell and in operative connection.
  • both motors are activated in synchronous mode (the relative movement of both motor bells to each other is zero), the airbrakes are set to a neutral position.
  • This mode of operation can be referred to as zero attack angle, and is comparable to a fixed propeller.
  • both motors or motor halves are activated in phase shift mode (one of the two motor bells rotates relatively decelerated), the propeller blades adapt to the new situation, remain in the new position and the new angle of attack is set.
  • Phase angle can be set as a positive or negative propeller blade angle. This principle can be used both for propeller screws for aircraft application, as well as for propellers for watercraft.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Valve Device For Special Equipments (AREA)
  • Vehicle Body Suspensions (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Système d'entraînement doté
    d'une hélice à pas variable avec un axe de symétrie présentant au minimum deux pales pivotant sur leur axe longitudinal permettant le réglage de l'angle d'incidence des pales et dotées d'une roue dentée,
    de deux roues motrices dentées situées sur l'axe de symétrie, chacune emboîtée d'un côté dans les roues dentées situées sur les pales ainsi que
    de deux moteurs électriques reliés chacun à l'une des roues motrices dentées.
  2. Système d'entraînement selon la revendication 1 caractérisé en ce que trois pales ou plus sont prévues.
  3. Système d'entraînement selon la revendication 1 ou 2 caractérisé en ce que les roues dentées sur les pales et les deux roues motrices dentées sont des roues coniques.
  4. Système d'entraînement selon la revendication 1 ou 2 caractérisé en ce que les roues dentées sur les pales sont des roues d'engrenage et les deux roues motrices dentées sont des roues de champ.
  5. Système d'entraînement selon les revendications de 1 à 4 caractérisé en ce que les roues dentées sur les pales sont situées à l'extrémité extérieure des pales et que les roues motrices dentées sont de forme toroïdale.
  6. Système d'entraînement selon la revendication 5 caractérisé en ce que les moteurs électriques sont des rotors internes sans balais dont chacun des rotors est relié aux roues motrices dentées de sorte que les enroulements statoriques des moteurs électriques sont situés en dehors de la zone de balayage des pales.
  7. Système d'entraînement selon les revendications de 1 à 4 caractérisé en ce que les roues dentées des pales sont situées à l'extrémité des pales face à l'axe de symétrie.
  8. Système d'entraînement selon la revendication 7 caractérisé en ce que les moteurs électriques sont des rotors externes sans balais dont chacun des rotors est relié à une roue motrice dentée de sorte que les enroulements statoriques des moteurs électriques sont situés à l'intérieur de la zone de balayage des pales.
  9. Système d'entraînement selon la revendication 7 ou 8 caractérisé en ce que les rotors des deux moteurs électriques sont situés sur un même axe creux.
  10. Système d'entraînement selon les revendications de 7 à 9 caractérisé en ce que les deux roues motrices dentées sont intégralement conçues avec les cloches des deux rotors.
  11. Système d'entraînement selon les revendications de 1 à 10 caractérisé en ce qu'une commande électrique est prévue pour la commande des moteurs électriques.
  12. Système d'entraînement selon la revendication 11 caractérisé en ce que la commande électrique présente des détecteurs angulaires pour le réglage de l'angle des moteurs électriques.
  13. Système d'entraînement selon la revendication 12 caractérisé en ce que les détecteurs angulaires comprennent des capteurs de passage à zéro.
  14. Système d'entraînement selon les revendications de 1 à 13 caractérisé en ce que les moteurs électriques puissent être également actionnés à l'aide d'un générateur.
  15. Système d'entraînement selon les revendications de 1 à 14 caractérisé en ce que les pales présentent un profil asymétrique.
EP07016481A 2007-08-22 2007-08-22 Système de propulsion avec une hélice à pas variable Not-in-force EP2028099B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP07016481A EP2028099B1 (fr) 2007-08-22 2007-08-22 Système de propulsion avec une hélice à pas variable
DE502007005052T DE502007005052D1 (de) 2007-08-22 2007-08-22 Antriebssystem mit einem Verstellpropeller
AT07016481T ATE481312T1 (de) 2007-08-22 2007-08-22 Antriebssystem mit einem verstellpropeller

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07016481A EP2028099B1 (fr) 2007-08-22 2007-08-22 Système de propulsion avec une hélice à pas variable

Publications (2)

Publication Number Publication Date
EP2028099A1 EP2028099A1 (fr) 2009-02-25
EP2028099B1 true EP2028099B1 (fr) 2010-09-15

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EP07016481A Not-in-force EP2028099B1 (fr) 2007-08-22 2007-08-22 Système de propulsion avec une hélice à pas variable

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EP (1) EP2028099B1 (fr)
AT (1) ATE481312T1 (fr)
DE (1) DE502007005052D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102574576A (zh) * 2009-10-22 2012-07-11 斯奈克玛 采用无刷电机改变飞机涡轮发动机螺旋桨叶片迎角的装置
EP4369576A1 (fr) * 2022-11-10 2024-05-15 YourSky Management Machine à induction avec mécanisme d'angle de pale variable

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CN103043199B (zh) * 2013-01-17 2015-05-13 苏州船用动力系统股份有限公司 轮缘式差动端面齿调距推进装置
NO342415B1 (en) * 2016-08-31 2018-05-22 FLIR Unmanned Aerial Systems AS Controlling blade pitch by a plurality of electric motors
JP2020531366A (ja) * 2017-08-23 2020-11-05 ヴィマアン ロボティクス， インコーポレイテッド 駆動機構
US10988247B2 (en) * 2017-10-19 2021-04-27 Uvionix Aerospace Corporation Unmanned aerial vehicle and propulsion system for an unmanned aerial vehicle
KR102651105B1 (ko) 2017-11-14 2024-03-27 플라이보틱스 에스아 2자유도 액추에이터를 형성하는 시스템으로서, 예를 들면 회전 중 프로펠러의 블레이드의 피치 각도를 변화시키기 위한 시스템
CN108995793B (zh) * 2018-09-03 2020-06-16 南京航空航天大学 一种旋翼变距系统
CN110861453B (zh) * 2019-11-15 2022-10-21 上海交通大学 可变输出转矩和螺距的跨介质水空两用推进装置
CN113212745A (zh) * 2021-04-26 2021-08-06 南方科技大学 一种旋翼无人机及该旋翼无人机的续航延长方法

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Publication number Priority date Publication date Assignee Title
DE2404694C3 (de) 1974-02-01 1982-02-11 Neuhierl, Hermann, Dr., 8510 Fürth Verstell-Luftschraube für Modellflugzeuge
US4556366A (en) * 1983-10-17 1985-12-03 General Electric Company Propeller actuation system
US5967749A (en) 1998-01-08 1999-10-19 Electric Boat Corporation Controllable pitch propeller arrangement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102574576A (zh) * 2009-10-22 2012-07-11 斯奈克玛 采用无刷电机改变飞机涡轮发动机螺旋桨叶片迎角的装置
CN102574576B (zh) * 2009-10-22 2015-12-09 斯奈克玛 采用无刷电机改变飞机涡轮发动机螺旋桨叶片迎角的装置
EP4369576A1 (fr) * 2022-11-10 2024-05-15 YourSky Management Machine à induction avec mécanisme d'angle de pale variable
WO2024099601A1 (fr) * 2022-11-10 2024-05-16 Yoursky Management Machine à induction dotée d'un mécanisme à angle de pale variable

Also Published As

Publication number Publication date
ATE481312T1 (de) 2010-10-15
EP2028099A1 (fr) 2009-02-25
DE502007005052D1 (de) 2010-10-28

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